Aircraft air conditioning system and method of operating an aircraft air conditioning system
This invention relates to an aircraft air conditioning system with at least one compressor, a first conduit connected with a pressure side of the compressor and at least one cooling unit provided downstream of the compressor. A second bypass conduit is connected with the pressure side of the compressor to conduct at least part of the compressed air around at least one cooling unit and has a throttle for varying air flow therethrough.
Latest Liebherr-Aerospace Lindenberg GmbH Patents:
This invention relates to an aircraft air conditioning system with at least one compressor, comprising a first conduit which is connected with the pressure side of the compressor and in which one or more cooling means provided downstream of the compressor are arranged for cooling the air compressed in the compressor, and comprising a second conduit designed as bypass conduit, which likewise is connected with the pressure side of the compressor and is arranged such that it conducts at least part of the air compressed in the compressor in a bypass around at least one of the cooling means, wherein a throttle means is arranged in the bypass conduit, by means of which the mass flow of the air conducted through the bypass conduit can be varied.
Aircraft air conditioning systems, which include compressors supplied with ambient air or precompressed air, are known in a number of different embodiments. A problem of electrically driven aircraft air conditioning systems for fresh air supply, air conditioning and pressurization consists in that with a specified mass flow rate, the pressure conditions on the compressor outlet side are changed due to the adjustment of the throttle means arranged in the bypass conduit, which in turn leads to the fact that the temperature of the compressed air is changed as well.
In summary it should be noted that in prior art systems a reproducible correlation between the variation of the opening of the throttle means provided in the bypass conduit on the one hand and the change in temperature realized thereby on the other hand does not exist or can only be realized with difficulty. Therefore, it is the object of the invention to develop an aircraft air conditioning system of the type mentioned above such that the temperature control or temperature regulation is simplified by varying the opening of the throttle means provided in the bypass conduit.
SUMMARY OF THE INVENTIONThis object is solved by an aircraft air conditioning system with the features herein.
Accordingly, it is provided that also in the first conduit, which includes said cooling means, a throttle means is arranged, by means of which the mass flow of the air conducted through the first conduit can be varied.
In accordance with the invention a unit is provided, which can be operated in a first and/or in a second operating mode. The unit can be designed such that it can be operated exclusively in the first operating mode. It can also be designed such that it can be operated exclusively in the second operating mode. In a further alternative, it can also be designed such that it can selectively be operated in the first or in the second operating mode.
The unit is designed such that in the first operating mode, when the opening of the throttle means provided in the bypass conduit is increased, it effects a reduction of the opening of the throttle means provided in the first conduit and, inversely, when the opening of the throttle means provided in the bypass conduit is reduced, it effects an increase of the opening of the throttle means provided in the first conduit. Due to the creation of a throttle means in the mass flow, which is directed over the cooling means, it is possible to make the conditions at the compressor outlet such that the variation of the opening of the throttle means arranged in the bypass conduit does not or only insignificantly lead to a change in the level of the compressor outlet pressure. In this way, a constant reproducible connection between the valve position of the throttle means of the bypass conduit and the temperature of the air flow supplied to the mixing chamber or aircraft cabin can be achieved.
In the second operating mode, the unit effects an increase of the opening of the throttle means provided in the bypass conduit and an increase of the opening of the throttle means provided in the first conduit or a reduction of the opening of the throttle means provided in the bypass conduit and a reduction of the opening of the throttle means provided in the first conduit. Such operating mode can be chosen when the transmittance of the aircraft air conditioning system should be controlled or regulated. When the transmittance of the aircraft air conditioning system should be increased, the openings of both throttle means are increased; when the transmittance of the aircraft air conditioning system should be reduced, the openings of both throttle means are reduced.
It is likewise conceivable that the unit is designed such that in principle it can be operated in both operating modes, i.e. if necessary in a temperature regulation mode or temperature control mode (first operating mode) and if necessary in a transmittance regulation mode or transmittance control mode (second operating mode). The choice of the operating mode can depend for instance on the ambient conditions in ground operation or during the flight.
In a further aspect of the invention it is provided that the change of the openings of the throttle means is effected such that the pressure at the compressor outlet remains constant or substantially constant when the openings are changed. In contrast to prior art aspects it is thus provided that a variation of the compressor outlet pressure is prevented or largely prevented by changing the opening of the throttle means provided in the bypass conduit.
Preferably, the unit is designed as a temperature control unit. One or more temperature sensors connected with this control unit can be provided, which measure the temperature of the air at a suitable point in the aircraft air conditioning system, the temperature control unit being designed such that upon detection of a deviation between actual and desired value it varies the opening of the throttle means provided in the bypass conduit for the purpose of reducing the deviation between actual and desired value. In accordance with the invention, there is also effected a variation of the opening of the throttle means provided in the first conduit.
It is conceivable for instance that the temperature sensor is arranged downstream of the opening of the bypass conduit into the first conduit, i.e. detects the mixing temperature, and that this value is used as variable to be controlled. Of course, other arrangements of the temperature sensor are also conceivable.
In particular, the temperature sensor can also be arranged before, i.e. upstream of the orifice point of the bypass conduit opening into the first conduit.
Said cooling means provided in the first conduit can be formed by a ram-air heat exchanger, which is cooled by ram or ambient air, and/or by a vapor cycle and/or by a turbine for expanding air compressed in the compressor.
In the first conduit, there can be arranged a turbine for expanding the air compressed in the compressor and a water separation circuit upstream of the turbine.
In a further aspect of the invention it is provided that in the first conduit a turbine is arranged for expanding air compressed in the compressor, and that the turbine with the compressor is seated on a shaft and forms an air cycle machine.
The compressor can be power-operated, wherein the motor likewise can be seated on the shaft on which the compressor and the turbine are provided.
In principle, the compressor can be of the one-stage or multi-stage type. It is conceivable that the compressor is formed by a plurality of compressor units, which are of the one-stage or multi-stage type and are arranged separately one behind the other or are connected with each other by a shaft. In a further aspect of the invention it can be provided that between the compressors or between the compressor stages an intermediate cooling is provided. Embodiments without such intermediate cooling are of course also conceivable.
Apart from said compressor, one or more further power-operated compressors can be provided, which are operable independent of the compressor and parallel thereto.
In a further aspect of the invention it is provided that the two throttle means are designed as separate components or as a uniform component. It is conceivable for instance that this uniform component constitutes a valve, which can change the transmittance through the first conduit and the transmittance through the bypass conduit at the same time. For instance, a plunger is conceivable, which can be reciprocated such that when moving in one direction it reduces the transmittance of the first conduit and at the same increases the transmittance of the bypass conduit, and when moving in the other direction reduces the transmittance through the bypass conduit and increases the transmittance through the first conduit. For this purpose, any design of such valve is conceivable, for instance also a conical design of a valve plunger or valve seat, by means of which any characteristic can be realized, such as the transmittance of the throttle means depends on the position of the plunger or valve body.
In a further aspect of the invention it is provided that a mass flow control unit is provided for controlling the mass flow through the aircraft air conditioning system, wherein there are provided one or more flow rate measuring means connected with the mass flow control unit as well as actuators by means of which the mass flow can be varied.
The actuators can be formed by means for adjusting the speed of a motor driving the compressor.
The mass flow control unit and the temperature control unit can be formed by different components or also by one and the same processor or controller.
The aircraft air conditioning system can include a turbine for expanding the air compressed in the compressor, and the bypass conduit can open into the first conduit downstream of the turbine. In principle, other orifice points are also conceivable.
In a further aspect of the invention it is provided that the aircraft air conditioning system includes a turbine for expanding the air compressed in the compressor and a condenser, which is provided downstream of the turbine such that the turbine outlet air traverses the cold side of the condenser, and that the bypass conduit opens into the first conduit downstream of the condenser.
Furthermore, it can be provided that in the first conduit a ram-air heat exchanger and a water separation circuit are arranged, and that the throttle means arranged in the first conduit is arranged upstream of the ram-air heat exchanger between the ram-air heat exchanger and the water separation circuit or is provided downstream of the water separation circuit.
In a further aspect of the invention it is provided that a connecting conduit is arranged, which connects the outlet of the compressor(s) with the inlet thereof, and that in the connecting conduit a valve is arranged, by means of which the mass flow of the air flowing through the connecting conduit can be changed. There can be provided a further control unit, which controls the temperature of the compressor outlet air, wherein the actual temperature value is detected by a temperature sensor and wherein the valve of the connecting conduit serves as an actuator.
The throttle means provided in the first conduit can also be formed by a variable turbine nozzle. Thus, it is conceivable that the change in the transmittance or mass flow rate is performed by the turbine nozzle, which involves the advantage that no additional elements or throttle means must be provided. Thus, the turbine nozzle alone can effect the change in the transmittance of the first conduit. It is also conceivable to provide a plurality of nozzle means, one of which is formed by the variable turbine nozzle, so that the function of varying the transmittance or the mass flow rate is also performed by the variable turbine nozzle.
The term “throttle means” thus not only refers to elements which “destroy” energy, such as a valve, but also those which convert the energy, such as said turbine nozzle.
The invention furthermore relates to a method with the features herein. Preferred aspects of the method are also the subject matter herein.
Further details and advantages of the invention will be explained in detail with reference to an embodiment illustrated in the drawing, in which:
Subsequent to this branching, the first conduit 10 includes a throttle means TCV_C, by means of which the mass flow through the first conduit can be varied. Downstream of this throttle means, the ram-air heat exchanger HX is provided, which is traversed by ram or ambient air and on its warm side is traversed by the compressor outlet air, which undergoes cooling in the heat exchanger HX.
The mass flow of the ambient or ram air is varied by means of the valve RAV provided on the ram air side, as is indicated in
The compressed air cooled in the ram-air heat exchanger HX then flows into the reheater REH and subsequently into the condenser COND, in which water in the compressed air is condensed. The water is separated in the downstream water separator WE. The air dehumidified in this way then flows through the reheater REH, where it is slightly heated, and then into the turbine T, in which it is expanded and thereby undergoes a considerable decrease in temperature. The air cooled in this way then flows through the cold side of the condenser COND. Subsequently, it is supplied to a mixing chamber or the aircraft cabin.
As is furthermore shown in
Reference numeral 30 designates temperature sensors, one of which is disposed downstream of the condenser COND. Due to its arrangement, it measures the temperature of the mixed air, which consists of the air conducted through the bypass conduit 20 and the air conducted through the first conduit 10. As shown in
Alternatively or in addition, a further temperature sensor 30 can be provided, which is disposed between the water separator WE and the reheater REH, as shown in
As can furthermore be taken from
The operation of the arrangement shown in
If the one or more temperature sensors 30 indicate an actual temperature value which lies below a desired temperature value, the temperature control unit ECU effects an increase of the opening of the throttle means or the throttle valve TCV_H arranged in the bypass conduit 20, which leads to the fact that warmer air is supplied in the mixing point. At the same time, however, the temperature control unit effects that the transmittance of the throttle means TCV_C provided in the first conduit 10 is reduced, so that the pressure conditions at the compressor outlet remain constant or largely constant. Thus, it is the function of the valve TCV_C to prevent or compensate a pressure drop at the compressor outlet, which in prior art systems would be caused by opening the valve TCV_H, which is effected by correspondingly reducing the transmittance through the valve TCV_C. The corresponding reverse process takes place when the valve TCV_H is throttled.
This leads to the fact that the pressure conditions at the compressor outlet are largely independent of the opening condition or the transmittance of the valve TCV_H provided in the bypass conduit 20. These conditions are schematically illustrated in
Thus, the pressure at the compressor outlet is independent of the degree of opening of the valve TCV_H, and a continuous and reliable temperature control is possible by means of the actuator TCV_H.
As can furthermore be taken from
Parallel to the control of the temperature, a flow-rate control is provided, as is likewise shown in
As can furthermore be taken from
In addition to the first compressor C1, there is provided a further compressor C2 supplied with ambient or ram air or precompressed air, which is driven by a second motor M2. In the compressor outlet conduits of both compressors C1, C2, check valves PCKV1 and PCKV2 are provided. Finally, the two compressor outlets are combined. The compressed air combined in this way is passed over the unit OZC, which is a converter for ozone and/or hydrocarbons. By means of the sensor 40, the flow rate of the compressed air is detected and used for flow-rate control by means of the unit ECU, which in the case of a deviation from the desired value changes the speed of the motor M1. As has already been explained with respect to
As can furthermore be taken from
In addition to the arrangement shown in
As can likewise be taken from
In the arrangement shown in
Claims
1. An aircraft air conditioning system with at least one compressor (C), comprising
- a first conduit (10) which is connected with the pressure side of the compressor (C) and in which one or more cooling means provided downstream of the compressor (C) are arranged for cooling the air compressed in the compressor (C),
- a single turbine (T) arranged in the first conduit (10), and
- a second conduit designed as bypass conduit (20), which is connected with the pressure side of the compressor (C) and arranged such that it conducts at least part of the air compressed in the compressor (C) in a bypass around at least one of the cooling means and with said single turbine (T) arranged in said first conduit (10) just upstream of the return junction with said second conduit (20), wherein
- a bypass throttle means (TCV_H) is arranged in the bypass conduit (20), by which the mass flow of the air conducted through the bypass conduit (20) can be varied,
- in the first conduit (10) a first throttle means (TCV_C, VTN) is arranged, by which the mass flow of the air conducted through the first conduit (10) can be varied,
- a single unit (ECU) is provided, which is designed such that it can be operated in a first operating mode, second operating mode, or both first and second operating modes,
- in the first operating mode, when opening of the bypass throttle means (TCV_H) provided in the bypass conduit (20) is increased, the unit (ECU) effects reduction of opening of the first throttle means (TCV_C, VTN) provided in the first conduit (10),
- inversely, when opening of the bypass throttle means (TCV_H) provided in the bypass conduit (20) is reduced, the unit (ECU) effects increase of opening of the first throttle means (TCV_C, VTN) provided in the first conduit (10),
- in the second operating mode, the unit (ECU) effects increase of opening of both the bypass throttle means (TCV_H) provided in the bypass conduit (20) and first throttle means (TCV_C, VTN) provided in the first conduit (10) or reduction of opening of both the bypass throttle means (TCV_H) provided in the bypass conduit (20) and first throttle means (TCV_C, VTN) provided in the first conduit (10), and
- with pressure at an outlet of said compressor (C) remaining essentially constant in all said operating modes.
2. The aircraft air conditioning system according to claim 1, wherein the unit (ECU) is designed such that the change of the openings of both throttle means (TCV_C, TCV_H) is effected with a pressure at the compressor outlet remaining constant when the openings are changed.
3. The aircraft air conditioning system according to claim 1, wherein the compressor (C) is arranged such that it is supplied with ambient or ram air or with precompressed air.
4. The aircraft air conditioning system according to claim 1, wherein the unit (ECU) is designed as a temperature control unit operating in the first operating mode and that there are provided one or more temperature sensors (30) connected with the temperature control unit, which measure the temperature of the air in the aircraft air conditioning system, wherein the temperature control unit is designed such that upon detection of a deviation between the actual temperature value measured by the temperature sensor(s) (30) and a specified desired temperature value it varies the opening of the throttle means (TCV_H) provided in the bypass conduit (20) for the purpose of reducing the control deviation.
5. The aircraft air conditioning system according to claim 4, wherein the bypass conduit (20) opens into the first conduit (10) and the one or more temperature sensors (30) in the first conduit (10) are arranged before, behind or both before and behind an orifice point of the bypass conduit (20) opening into the first conduit (10).
6. The aircraft air conditioning system according to claim 1, wherein the cooling means provided in the first conduit (10) are formed by a heat exchanger (HX) cooled with ram or ambient air and/or by a vapor cycle and/or by a turbine (T) for expanding air compressed in the compressor (C).
7. The aircraft air conditioning system according to claim 1, wherein the turbine (T) expands air compressed in the compressor (C) and a water separation circuit is provided upstream of the turbine (T).
8. The aircraft air conditioning system according to claim 1, wherein the turbine (T) and compressor (C) are seated on a shaft.
9. The aircraft air conditioning system according to claim 8, wherein the compressor (C), the turbine (T) and a motor (M) are all seated on the shaft.
10. The aircraft air conditioning system according to claim 1, wherein at least one motor (M) connected with the compressor (C) is provided for driving the compressor (C).
11. The aircraft air conditioning system according to claim 1, wherein the compressor (C) is of the one-stage or multi-stage type.
12. The aircraft air conditioning system according to claim 1, wherein the throttle means (TCV_H) provided in the bypass conduit (20) and the throttle means (TCV_C) provided in the first conduit (10) are designed as separate components or are formed by one common assembly.
13. The aircraft air conditioning system according to claim 1, wherein a mass flow control unit (ECU) is provided for controlling the mass flow through the aircraft air conditioning system, one or more flow rate measuring means (40) connected with the mass flow control unit as well as actuators are provided, by which the mass flow can be varied.
14. The aircraft air conditioning system according to claim 13, wherein the actuator(s) is(are) formed by means for adjusting the speed of a motor (M) driving the compressor (C).
15. The aircraft air conditioning system according to claim 13, wherein the mass flow control unit (ECU) and the temperature control unit (ECU) are formed by different components or by a controller.
16. The aircraft air conditioning system according to claim 1, wherein the bypass conduit (20) opens into the first conduit (10) downstream of the turbine (T).
17. The aircraft air conditioning system according to claim 1, configured such that in the first operating mode, pressure at the pressure side of the compressor (C) remains substantially constant and independent of degree of opening of the bypass throttle means (TCV_H), and
- in the second operating mode, transmittance of air conditioning is respectively increased or reduced.
18. The aircraft air conditioning system according to claim 1, additionally comprising
- at least one temperature sensor (30) arranged to indicate actual temperature value and forward the same to said unit (ECU), wherein
- said unit (ECU) is configured to open or close said bypass throttle means (TCV_H) when the actual temperature value is below or above a desired temperature value and, at the same time, close or open said first throttle means (TCV_C) to maintain the pressure at the outlet of said compressor (C) substantially constant.
19. A method of operating an aircraft air conditioning system, in particular an aircraft air conditioning system with a compressor (C), comprising
- a first conduit (10) which is connected with the pressure side of the compressor (C) and in which one or more cooling means provided downstream of the compressor (C) are arranged for cooling the air compressed in the compressor (C),
- a single turbine (T) arranged in the first conduit, and
- a second conduit designed as bypass conduit (20), which is connected with the pressure side of the compressor (C) and arranged such that it conducts at least part of the air compressed in the compressor (C) in a bypass around at least one of the cooling means and with said single turbine (T) arranged in said first conduit (10) just upstream of the return junction with said second conduit (20), wherein
- a bypass throttle means (TCV_H) is arranged in the bypass conduit (20), by which the mass flow of the air conducted through the bypass conduit (20) can be varied,
- in the first conduit (10) a first throttle means (TCV_C, VTN) is arranged, by which the mass flow of the air conducted through the first conduit (10) can be varied,
- a single unit (ECU) controls opening and closing of both said first and bypass throttle means (TCV_C, VTN: TCV_H), and
- when increasing an opening of the bypass throttle means (TCV_H) provided in the bypass conduit (20) a reduction of an opening of the first throttle means (TCV_C, VTN) provided in the first conduit (10) is effected and,
- inversely, when reducing the opening of the bypass throttle means (TCV_H) provided in the bypass conduit (20) an increase of the opening of the throttle means (TCV_C, VTN) provided in the first conduit (10) is effected, or
- when increasing the opening of the bypass throttle means (TCV_H) provided in the bypass conduit (20) an increase of the opening of the throttle means (TCV_C, VTN) provided in the first conduit (10) is effected, and
- when reducing the opening of the bypass throttle means (TCV_H) provided in the bypass conduit (20), a reduction of the opening of the first throttle means (TCV_C, VTN) provided in the first conduit (10) is effected,
- such that pressure at an outlet of said compressor (C) remains essentially constant in all said opening and closing combinations of said first and bypass throttle means (TCV_C, VTN; TCV_H).
20. The method according to claim 19, wherein the openings of the throttle means (TCV_C, TCV_H) are changed such that the pressure at the compressor outlet is not changed by changing the openings of the throttle means (TCV_C, TCV_H).
21. The method according to claim 19, wherein the temperature of the air flowing through the aircraft air conditioning system is measured and compared with a desired value, and in the case of a deviation between desired value and actual value, a change of the opening of the throttle means (TCV_H) provided in the bypass conduit (20) is performed for the purpose of temperature control.
22. The method according to claim 21, wherein the bypass conduit (20) opens into the first conduit (10) at an orifice point, and the temperature measurement is performed downstream or upstream of the orifice point.
23. The method according to claim 21, wherein the aircraft air conditioning system has a water separation circuit including a reheater (REH), condenser (COND), and water separator (WE), and the temperature measurement is effected between the water separator (WE) and the reheater (REH).
24. The method according to claim 19, wherein independent of the temperature control a control of the mass flow of the compressor outlet air is effected.
Type: Grant
Filed: Jul 16, 2007
Date of Patent: Feb 5, 2013
Patent Publication Number: 20080032616
Assignee: Liebherr-Aerospace Lindenberg GmbH (Lindenberg/Allgäu)
Inventor: Franz Martin Vögel (Lindenberg)
Primary Examiner: Marc Norman
Assistant Examiner: Filip Zec
Application Number: 11/879,055
International Classification: F25D 9/00 (20060101); F25B 9/00 (20060101); B64D 13/02 (20060101);